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Measurement of corner separation zone response on a compression ramp to plasma actuation within the hypersonic boundary layer
2017
IOP Conference Series: Materials Science and Engineering
This study was performed to characterize the dominant frequencies present in the boundary layer uptsream of and in the corner separation zone of a compression surface in Mach 4.5 flow and to determine a control effect of transient plasma actuation on the boundary layer. Schlieren imaging was used to distinguish the corner separation zone for 20°, 25°, and 30° compression ramps mounted on flat plates. Spectra of the natural disturbances present in the boundary layer and separation zone were
doi:10.1088/1757-899x/249/1/012013
fatcat:hctpd6uqgfgibfzt3acmytb64q